EP3301288B1 - Boîte de vitesses accessoire pour moteur à turbine à gaz - Google Patents

Boîte de vitesses accessoire pour moteur à turbine à gaz Download PDF

Info

Publication number
EP3301288B1
EP3301288B1 EP17194297.2A EP17194297A EP3301288B1 EP 3301288 B1 EP3301288 B1 EP 3301288B1 EP 17194297 A EP17194297 A EP 17194297A EP 3301288 B1 EP3301288 B1 EP 3301288B1
Authority
EP
European Patent Office
Prior art keywords
engine
nacelle
casing
bypass
accessory gearbox
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17194297.2A
Other languages
German (de)
English (en)
Other versions
EP3301288A1 (fr
Inventor
Uwe Minkus
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3301288A1 publication Critical patent/EP3301288A1/fr
Application granted granted Critical
Publication of EP3301288B1 publication Critical patent/EP3301288B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/90—Mounting on supporting structures or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/90—Mounting on supporting structures or systems
    • F05D2240/91—Mounting on supporting structures or systems on a stationary structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present disclosure concerns accessory gearboxes for gas turbine engines, and in particular arrangements for mounting such gearboxes.
  • a gas turbine engine is generally indicated at 10, having a principal and rotational axis 11.
  • the engine 10 comprises, in axial flow series, an air intake 12, a propulsive fan 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, a low-pressure turbine 17 and an exhaust nozzle 18.
  • the engine 10 is surrounded by a casing 20; typically the casing 20 comprises a fan casing 40, an intermediate casing (IMC) or intermediate compressor casing (ICC) 42 and a bypass casing 44.
  • the casings 40, 42 and 44 are coaxial and are typically joined axially to one another by flanges (not shown) to form the casing 20.
  • the outer contours of the fan casing 40, IMC or ICC 42 and bypass casing 44 together define an engine outer casing line.
  • the fan casing 40 defines the air intake 12; the bypass casing defines a bypass duct 21.
  • the gas turbine engine 10 works in the conventional manner so that air entering the intake 12 is accelerated by the fan 13 to produce two air flows: a first air flow into the high-pressure compressor 14 and a second air flow which passes through the bypass duct 21 to provide propulsive thrust.
  • the high-pressure compressor 14 compresses the air flow directed into it before delivering that air to the combustion equipment 15.
  • the air flow is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive the high and low-pressure turbines 16, 17 before being exhausted through the nozzle 18 to provide additional propulsive thrust.
  • the high 16 and low 17 pressure turbines drive respectively the high pressure compressor 14 and the fan 13 by suitable interconnecting shafts 22, 23.
  • the high-pressure compressor 14, combustion equipment 15 and high-pressure turbine 16 together constitute the core engine.
  • gas turbine engines to which the present disclosure may be applied may have alternative configurations.
  • such engines may have an alternative number of interconnecting shafts (e.g. three) and/or an alternative number of compressors and/or turbines.
  • the engine may comprise a gearbox provided in the drive train from a turbine to a compressor and/or fan.
  • Accessory units provide power for aircraft hydraulic, pneumatic and electrical systems, in addition to providing various pumps and control systems for efficient engine operation.
  • the drive for the accessory units is typically taken from one of the engine rotating shafts 22, 23, via an internal gearbox (not shown in Figure 1 ) to an external - or accessory - gearbox (not shown) which is typically mounted on the outside of the fan casing or intermediate casing (IMC) or intermediate compressor casing (ICC).
  • the accessory gearbox provides a mounting for the accessory units and distributes an appropriate geared drive to each accessory unit.
  • Other components may also be mounted on the engine casings and may protrude radially outward beyond the engine outer casing line.
  • the dressed engine i.e.
  • the engine together with the accessory gearbox, accessory units and any other components mounted on the engine casings) is surrounded by a nacelle (not shown in Figure 1 ) which protects the components and defines a nacelle outer contour which provides an aerodynamically smooth outer surface for the power plant.
  • the accessory gearbox extends circumferentially around the fan casing or IMC, and the individual accessory units are mounted to it so that they extend mostly axially.
  • the accessory gearbox will extend about one-quarter to one-third of the way around the circumference of the engine.
  • the accessory gearbox Due to the size of the accessory gearbox and the size of the accessories it drives, the accessory gearbox defines the nacelle outer contour. Because the nacelle outer contour in turn defines the aerodynamic shape of the nacelle, also known as the loft lines, it also in effect defines the overall length of the nacelle - the larger the nacelle outer contour, the longer must be the nacelle. The size of the accessory gearbox and its protrusion radially outward from the dressed engine therefore increase both the nacelle outer contour and the nacelle length, with an inevitable increase in the weight of the nacelle and in its drag in operation.
  • United States patent application number US2012/0117981A1 disclose arrangements for mounting accessory gearboxes on gas turbine engines.
  • FIG 2(a) shows a gas turbine engine 110 comprising a nacelle air intake 112, a fan casing 113, an IMC 114, and a core engine 180 mounted within a bypass casing 182.
  • an ICC may take the place of the IMC 114.
  • the core engine 180 and the bypass casing 182 together define an annular bypass duct 121.
  • air entering the nacelle air intake 112 is accelerated by a fan (not shown in Figure 2(a) ) to produce two air flows: a first air flow into the core engine 180 and a second air flow which passes through the bypass duct 121 to provide propulsive thrust.
  • the core engine air flow is exhausted through a nozzle 118; the bypass air flow is exhausted through a bypass nozzle 119 defined by a nacelle 120.
  • the accessories 190 may be of any known type (for example starter, hydraulic pump, heat exchanger, breather, oil pump, drains tank, hydro-mechanical unit (HMU), fuel pump, alternator).
  • starter hydraulic pump, heat exchanger, breather, oil pump, drains tank, hydro-mechanical unit (HMU), fuel pump, alternator.
  • HMU hydro-mechanical unit
  • the nacelle outer contour (i.e. the profile of the outer skin of the nacelle 120 around and along the whole engine) is constrained by the need to maintain a minimum clearance 196 between the dressed engine and the nacelle outer skin. Because the accessory gearbox 140 protrudes from the lower part of the IMC and because there is no corresponding protrusion from the upper part of the IMC, the lower part of the nacelle extends further away 198 from the bypass duct casing 182 than does the upper part 199, so that the outer contour of the nacelle 120 is non-circular. The nacelle outer contour along the lower part of the engine therefore constrains the loft lines and thereby the overall length 160 of the nacelle, which is greater than if it were constrained by the nacelle outer contour along the upper part of the engine.
  • Figure 2(b) shows a gas turbine engine 210.
  • the gas turbine engine 210 comprises a nacelle air intake 112, a fan casing 113, an IMC 114, and a core engine 180 mounted within a bypass casing 282.
  • the core engine 180 and the bypass casing 282 together define an annular bypass duct 121.
  • air entering the nacelle intake 112 is accelerated by a fan to produce two air flows: a first air flow into the core engine 180 and a second air flow which passes through the bypass duct 121 to provide propulsive thrust.
  • the core engine air flow is exhausted through a nozzle 118; the bypass air flow is exhausted through a bypass nozzle 219 defined by a nacelle 220.
  • the bypass casing 282 Mounted to the bypass casing 282 is an axially-aligned accessory gearbox 240, on which are mounted a number of accessories 290 (only three shown).
  • the accessories 290 may be of any known type, as described above.
  • the bypass casing 282 comprises a recess configured to accommodate the accessory gearbox 240, so that the accessory gearbox 240 is partially inset into the bypass casing 282 and protrudes less far in a radial direction than if the recess were not present.
  • bypass casing 282 The radially inward contouring of the bypass casing 282 to accommodate the accessory gearbox 240 results in a corresponding contouring on the inner wall of the bypass casing 282, which locally reduces the cross-sectional area of the bypass duct 121. This inevitably increases the bypass losses, but because the bypass flow velocity is lower than the flow velocity outside the nacelle, a geometrically identical blockage will cause less loss in the bypass and hence result in an overall reduced loss (at engine / power plant level).
  • bypass duct 121 inner wall formed by, for example, the fairings of the core engine 180 or inner fixed structure(not shown in Figure 2(b) ) so that there is no or less local reduction in the bypass duct 121 cross-sectional area.
  • the benefit of the axially mounted accessory gearbox can thus be maximised.
  • the axially-extending accessory gearbox 240 protrudes less far from the bypass casing 282 than does the conventional accessory gearbox 140 in the arrangement of Figure 2(a) . Therefore, the lower part of the nacelle 220 extends less far 298 from the bypass casing 282 than in the arrangement of Figure 2(a) .
  • the upper dimension 299 is the same as the corresponding dimension 199 in Figure 2(a) , so the outer casing line of the nacelle 220 is smaller than the outer casing line of the nacelle 120.
  • the overall length 260 of the nacelle 220 can be made shorter than the overall length 160 of the nacelle 120 without introducing aerodynamically unacceptable curvatures.
  • the reduced length and reduced outer casing line of the nacelle 220 deliver a significant reduction in weight compared with the conventional nacelle 120, and the reduced outer casing line also delivers an aerodynamic benefit.
  • bypass casing 282 may comprise no recess, so that the accessory gearbox 240 is simply mounted on the bypass casing 282. This will cause the accessory gearbox 240 to protrude further in a radial direction than in the arrangement of Figure 2(b) , and therefore the outer casing line will be larger than for the arrangement of Figure 2(b) .

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (2)

  1. Moteur à turbine à gaz, le moteur (210) comprenant une boîte d'entraînement des accessoires (240) alignée dans une direction axiale le long du moteur ; la boîte d'entraînement des accessoires étant montée sur un carter de dérivation (282) du moteur, le carter de dérivation définissant une paroi extérieure d'un conduit de dérivation (121) ; et la boîte d'entraînement des accessoires étant enfoncée au moins partiellement dans un creux du carter de dérivation, le creux entraînant une réduction de la section transversale du conduit de dérivation dans la région du creux ; une paroi intérieure du conduit de dérivation comprenant un creux correspondant pour atténuer la réduction de la section transversale.
  2. Moteur à turbine à gaz selon la revendication 1, l'alignement axial de la boîte d'entraînement des accessoires permettant une réduction de la ligne de carter extérieure d'une nacelle du moteur et donc une réduction de la longueur totale de la nacelle.
EP17194297.2A 2016-10-03 2017-10-02 Boîte de vitesses accessoire pour moteur à turbine à gaz Active EP3301288B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1616759.5A GB201616759D0 (en) 2016-10-03 2016-10-03 Accessory gearbox for a gas turbine engine

Publications (2)

Publication Number Publication Date
EP3301288A1 EP3301288A1 (fr) 2018-04-04
EP3301288B1 true EP3301288B1 (fr) 2019-10-02

Family

ID=57571210

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17194297.2A Active EP3301288B1 (fr) 2016-10-03 2017-10-02 Boîte de vitesses accessoire pour moteur à turbine à gaz

Country Status (3)

Country Link
US (1) US10968833B2 (fr)
EP (1) EP3301288B1 (fr)
GB (1) GB201616759D0 (fr)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7090165B2 (en) * 2003-06-02 2006-08-15 Rolls-Royce Plc Aeroengine nacelle
GB0315894D0 (en) * 2003-07-08 2003-08-13 Rolls Royce Plc Aircraft engine arrangement
US20060137355A1 (en) * 2004-12-27 2006-06-29 Pratt & Whitney Canada Corp. Fan driven emergency generator
US8312728B2 (en) 2007-06-28 2012-11-20 United Technologies Corporation Generator with separate oil system for improved nacelle performance
US8602717B2 (en) * 2010-10-28 2013-12-10 United Technologies Corporation Compression system for turbomachine heat exchanger
US8490410B2 (en) * 2010-11-17 2013-07-23 United Technologies Corporation Axial accessory gearbox
US9926849B2 (en) * 2011-06-14 2018-03-27 Honeywell International Inc. Transverse mounted accessory gearbox
DE102011112250A1 (de) * 2011-09-02 2013-03-07 Rolls-Royce Deutschland Ltd & Co Kg Hilfsgerätegetriebeeinrichtung für ein Triebwerk
US20140090386A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Geared turbofan with fan and core mounted accessory gearboxes
US20160230843A1 (en) 2015-02-09 2016-08-11 United Technologies Corporation Gearbox for gas turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US10968833B2 (en) 2021-04-06
EP3301288A1 (fr) 2018-04-04
US20180094717A1 (en) 2018-04-05
GB201616759D0 (en) 2016-11-16

Similar Documents

Publication Publication Date Title
EP3339607B1 (fr) Architecture de moteur à écoulement inverse
US8328504B2 (en) Aeroengine drain assembly
EP2060759B1 (fr) Turbine à gaz avec deux boîtiers d'entraînement d'accessoires
US10823080B2 (en) Dual accessory gearbox
JP4463810B2 (ja) 航空機用エンジン装置
CN108350755B (zh) 航空器涡轮机前部部分
CA2928979C (fr) Systeme de support d'arbres de rotor d'un moteur de turbo a entrainement direct
US20160237906A1 (en) Intercooled cooling air with heat exchanger packaging
JP6560418B2 (ja) ガスタービンエンジン
EP3187712B1 (fr) Admission courte de nacelle
US20170356347A1 (en) Accessory gearbox assembly and a gas turbine engine comprising an accessory gearbox assembly
CA3030249A1 (fr) Un assemblage de boite de vitesses et un moteur de turbine a gaz comportant un assemblage de boite de vitesses accessoire
CA2883088C (fr) Mesure directe a l'aide d'une pompe a palettes a deplacement variable
EP2917508B1 (fr) Turbine à gaz avec une fente d'air de prélèvement de compresseur
US20180216631A1 (en) Geared gas turbine engine
EP3536902B1 (fr) Composant de moteur à turbine à gaz
EP3109435B1 (fr) Air de refroidissement refroidi avec conditionnement d'échangeur de chaleur
EP3301288B1 (fr) Boîte de vitesses accessoire pour moteur à turbine à gaz
US10724390B2 (en) Collar support assembly for airfoils
US20230250733A1 (en) Turbine engine with a cowl door
EP2980385B1 (fr) Cône avec bride de retour d'avant rallongée sur l'arrière
CN116209821A (zh) 设置有螺旋桨和偏置定子轮叶的涡轮机模块

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20181130

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190719

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1186439

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017007444

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191002

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1186439

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200203

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200102

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200103

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200102

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200224

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017007444

Country of ref document: DE

PG2D Information on lapse in contracting state deleted

Ref country code: IS

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191002

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200202

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191031

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

26N No opposition filed

Effective date: 20200703

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20171002

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201031

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191002

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230528

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231024

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20231026

Year of fee payment: 7

Ref country code: DE

Payment date: 20231027

Year of fee payment: 7